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NACA M20 AIRFOIL

Cambered · 8% thick · low-to-mid Re
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PROFILENACA M20 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness8.1% @ 30%c
max camber6.1% @ 30%c
LE radius0.73%c
area upper / chord0.0637
area lower / chord0.0059
area camber / chord0.0348
TE thickness0.47%c
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Polars

Preliminary
NeuralFoil
-0.3149-50.38233.3331.07911.671.77720ClAngle of attack (°)
Why this curve

This is a NeuralFoil prediction from the stored profile coordinates and the selected flow condition, with AeroSandbox compressibility corrections. It is not a completed OpenFOAM calculation.

Prediction error has not been calibrated for this condition. No accuracy interval is claimed.

The compressibility correction is a low-fidelity estimate, not a resolved shock or compressible CFD solution.

Geometry fit: RMS error 0.06218% of chord; maximum error 0.3188%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
152.4
Angle at maximum lift / drag (°)
8
Minimum Cd
0.006486
Maximum Cl
1.602
Angle at maximum Cl (°)
10
Cd at zero lift
0.009703
Cm at zero angle
-0.05341
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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